A Model Reference Adaptive Control Approach to Terrain Following Flight Control System

Berk İnan; İbrahim Aliskan

Article Details

A Model Reference Adaptive Control Approach to Terrain Following Flight Control System

Authors:

Berk İnan | İbrahim Aliskan

Publisher:

Duzce University

Main Topics:

Kontrol Mühendisliği | Mekatronik ve Robotik (Diğer)

Journal:

Düzce Üniversitesi Bilim ve Teknoloji Dergisi Vol.13 Issue 2, pp.770-789

Document Type:

Article

Publication Date:

4/2025

Document Language:

English

Document ID (Org No.):

2001346576

pISSN:

2148-2446

Keywords:

Abstract:

 Automatic Flight Control System AFCS Terrain Following TF mode allows military aircraft to fly at a certain altitude above ground level at a low altitude. TF mode reduces the probability of aircraft detection by enemy airborne radars. TF mode minimizes the effort the pilot spends to control the aircraft and allows the pilot to focus on other tasks or missions. In this study, the F-16 nonlinear model is linearized around a selected equilibrium point. The state variables of the linear model are decomposed into state space matrices on the lateral and longitudinal axes. Three different control methods, namely PID Proportional-Integral-Derivative, LQR Linear Quadratic Regulator, and MRAC Model Reference Adaptive Control, are used. The results show that the designed algorithms can effectively control the aircrafts altitude, speed, pitch angle, angle of attack, and pitch rate on the longitudinal axis and the aircraft flies in accordance with the terrain profile. Finally, it is observed that MRAC outperforms PID and LQR methods due to its adaptive capability.

 Automatic Flight Control System AFCS Terrain Following TF mode allows military aircraft to fly at a certain altitude above ground level at a low altitude. TF mode reduces the probability of aircraft detection by enemy airborne radars. TF mode minimizes the effort the pilot spends to control the aircraft and allows the pilot to focus on other tasks or missions. In this study, the F-16 nonlinear model is linearized around a selected equilibrium point. The state variables of the linear model are decomposed into state space matrices on the lateral and longitudinal axes. Three different control methods, namely PID Proportional-Integral-Derivative, LQR Linear Quadratic Regulator, and MRAC Model Reference Adaptive Control, are used. The results show that the designed algorithms can effectively control the aircrafts altitude, speed, pitch angle, angle of attack, and pitch rate on the longitudinal axis and the aircraft flies in accordance with the terrain profile. Finally, it is observed that MRAC outperforms PID and LQR methods due to its adaptive capability.

 Automatic Flight Control System AFCS Terrain Following TF mode allows military aircraft to fly at a certain altitude above ground level at a low altitude. TF mode reduces the probability of aircraft detection by enemy airborne radars. TF mode minimizes the effort the pilot spends to control the aircraft and allows the pilot to focus on other tasks or missions. In this study, the F-16 nonlinear model is linearized around a selected equilibrium point. The state variables of the linear model are decomposed into state space matrices on the lateral and longitudinal axes. Three different control methods, namely PID Proportional-Integral-Derivative, LQR Linear Quadratic Regulator, and MRAC Model Reference Adaptive Control, are used. The results show that the designed algorithms can effectively control the aircrafts altitude, speed, pitch angle, angle of attack, and pitch rate on the longitudinal axis and the aircraft flies in accordance with the terrain profile. Finally, it is observed that MRAC outperforms PID and LQR methods due to its adaptive capability.

 Otomatik Uçuş Kontrol Sistemi OUKS Arazi Takibi modu askeri hava araçlarının alçak irtifada yer seviyesinin üzerinde belirli bir irtifada uçmasını sağlar. Arazi takip modu düşman radarları tarafından hava aracının tespit edilebilme olasılığını azaltır. Pilotun hava aracını kontrol etmesi için sarf ettiği iş gücünü azaltır ve pilotun diğer görevlere veya misyonlara odaklanmasına olanak tanır. Bu çalışmada, F-16 doğrusal olmayan modeli seçilen bir denge noktası etrafında doğrusallaştırılmıştır. Doğrusal modelin durum değişkenleri yatay ve dikey eksenlerde durum uzayı matrislerine ayrıştırılmıştır. PID Oransal-İntegral-Türevsel, LQR Doğrusal Kuadratik Regülatör ve MRAC Model Referans Uyarlamalı Kontrol olmak üzere üç farklı kontrol yöntemi kullanılmıştır. Sonuçlar, tasarlanan algoritmaların uçağın boylamasına eksendeki irtifa, hız, yunuslama açısı, hücum açısı ve yunuslama hızını etkili bir şekilde kontrol edebildiğini ve uçağın arazi profiline uygun şekilde uçtuğunu göstermektedir. Son olarak, MRACın adaptasyon kabiliyetinden dolayı PID ve LQR methotlarına üstünlük sağladığı gözlenmiştir.

Article Details

A Model Reference Adaptive Control Approach to Terrain Following Flight Control System

Authors:

Berk İnan | İbrahim Aliskan

Publisher:

Duzce University

Main Topics:

Kontrol Mühendisliği | Mekatronik ve Robotik (Diğer)

Journal:

Düzce Üniversitesi Bilim ve Teknoloji Dergisi Vol.13 Issue 2, pp.770-789

Document Type:

Article

Publication Date:

4/2025

Document Language:

English

Document ID (Org No.):

2001346576

pISSN:

2148-2446

MRAC

LQR

PID

Terrain Following

AFCS

F-16OUKS

F-16

LQR

MRAC

PID

Arazi Takibi

Issues

Article Details

Authors: Berk İnan | İbrahim Aliskan

Publisher: Duzce University

Main Topics: Kontrol Mühendisliği | Mekatronik ve Robotik (Diğer)

Journal: Düzce Üniversitesi Bilim ve Teknoloji Dergisi Vol.13 Issue 2, pp.770-789

Document Type: Article

Publication Date: 4/2025

Document Language: English

Document ID (Org No.): 2001346576

pISSN: 2148-2446

Issues

Authors:

Berk İnan | İbrahim Aliskan

Publisher:

Duzce University

Main Topics:

Kontrol Mühendisliği | Mekatronik ve Robotik (Diğer)

Journal:

Düzce Üniversitesi Bilim ve Teknoloji Dergisi Vol.13 Issue 2, pp.770-789

Document Type:

Article

Publication Date:

4/2025

Document Language:

English

Document ID (Org No.):

2001346576

pISSN:

2148-2446